Numerical simulations are performed to characterize the jet vane thrust vector control mounted in the rear of a rocket motor. The three-dimensional Navier—Stokes equations along with the K—ε turbulence model are solved in a hybrid mesh consisting of an unstructured grid and a structured grid. All essential flow features including the complex compression/expansion wave interactions emanating from the vane surfaces and shrouds are captured by simulation. The computed side force coefficients are seen to vary linearly with chamber pressure and vane deflection angles. A theoretical correlation has been developed by a non-linear regression analysis from the computational fluid dynamics (CFD) database to predict the force and moment coefficients for different chamber pressures, vane deflection angle, and roll offset angle. The theoretical correlation compare very well with full CFD simulation as well as the experimental data.

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The HETD (Hot End Technologies Directorate) of GTRE (Gas Turbine Research Establishment) has the mandate of design, development and delivery of airworthy combustor and afterburner modules for a military aero gas turbine engine. In order to meet the mandate, the directorate takes the overall responsibility of design to manufacture of the combustion systems. Three-dimensional CFD (Computational Fluid Dynamics) analyses played a vital role in arriving at the final configuration meeting the specific design targets. This paper focuses on the utilization of the CFD code ‘Fluent’ in the successful realization of the main combustor of an aero gas turbine engine.